CN117422610A - Three-dimensional model light weight method and device and electronic equipment - Google Patents
Three-dimensional model light weight method and device and electronic equipment Download PDFInfo
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Abstract
A three-dimensional model light weight method, a device and electronic equipment, wherein the method comprises the following steps: obtaining a derived model and a satellite coordinate system corresponding to the derived model, calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix, calculating a body coordinate system corresponding to the derived model, carrying out equidistant cutting on the derived model along a target direction in the body coordinate system to obtain a slice group, clustering the slice group according to a target clustering mode to obtain a slice group, determining a simplified model corresponding to the slice group, and processing the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model. By the method, the derived model is processed by adopting the preset cutting mode and the target clustering mode, the derived model is simplified while the derived model is disassembled, and the conversion efficiency from the derived model to the target model is improved.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a three-dimensional model light-weight method and device and electronic equipment.
Background
The satellite structure model relates to the coupling of a plurality of subsystem structures, in the process of electromagnetic compatibility simulation, thermal control simulation, mechanical simulation and the like, the forced decoupling mode is generally adopted to carry out the simulation design of the plurality of subsystem structures, and the satellite structure model needs to be simplified and designed in order to improve the simulation efficiency on the premise of ensuring the simulation precision due to the high fineness requirement of the satellite structure model.
The model design software is generally adopted to derive a derived model for simulation in a satellite structure model meeting simulation requirements, other simulation systems need to determine a lightweight model from the derived model, and since the data volume of a three-dimensional data model of the satellite structure model is quite large, a great deal of time is consumed for reading the derived model from the three-dimensional data model.
In addition, since the surface features of each single component in the derived model are highly refined and the local external details are complex, in order to improve the simulation efficiency by other simulation systems, the derived model needs to be simplified in the following manner: the staff carries out manual processing on the derived model for a plurality of times before the same simulation scene, so that a light-weight model corresponding to the derived model is obtained, the structure is simplified, the process is complicated, and a large amount of time is consumed.
In summary, how to quickly determine a lightweight model of a derived model from a three-dimensional data model becomes a major problem to be solved at present.
Disclosure of Invention
The application provides a three-dimensional model light-weight method, a device and electronic equipment, which are used for efficiently determining a light-weight model of a derived model from a three-dimensional data model.
In a first aspect, the present application provides a method for lightening a three-dimensional model, the method comprising:
obtaining a derived model and a satellite coordinate system corresponding to the derived model;
calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix, and calculating a body coordinate system corresponding to the derived model;
equidistant cutting is carried out on the derived model along the target direction in the body coordinate system to obtain a slice group, and the slice group is clustered according to a target clustering mode to obtain a slice group;
and determining a simplified model corresponding to the slice group, and processing the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model.
By the method, the derived model is equidistantly cut and clustered, pins, exposed cables and the like of the derived model are removed, the purpose of simplifying the derived model is achieved, the cut surfaces are classified, and the accuracy of the obtained target model is ensured.
In one possible design, the calculating, based on a preset cutting manner, a target attitude angle of the derived model in the satellite coordinate system, and bringing the target attitude angle into a preset rotation matrix, and calculating an ontology coordinate system corresponding to the derived model includes:
calculating the attitude angles of the derived model in each preset coordinate axis direction in the satellite coordinate system to obtain a plurality of attitude angles;
and screening out the target attitude angle with the highest appearance frequency from all the attitude angles, taking the target attitude angle into a preset rotation matrix, and calculating a body coordinate system corresponding to the derived model.
By the method, the attitude angles of the derived model in all axial directions are calculated, the target attitude angle is determined from all the attitude angles, and the accuracy of the target attitude angle is ensured, so that the accuracy of the determined body coordinate system is ensured.
In one possible design, the calculating the attitude angle of the derived model in each preset coordinate axis direction in the satellite coordinate system, to obtain a plurality of attitude angles, includes:
Acquiring the attitude angle of the derived model in the direction of a single preset coordinate axis in the satellite coordinate system, wherein the attitude angle comprises the following steps:
obtaining n planes, cutting the derived model along the m-th direction to obtain n cut sections, determining outer frames corresponding to the n cut sections, and determining the m-th attitude angle of the derived model in the single preset coordinate axis direction based on all the outer frames and the m-th direction, wherein n is 1 and 2, m is 1, 2 and 3, and the 1-th attitude angle, the 2-th attitude angle and the 3-th attitude angle are a plurality of attitude angles of the derived model in the single preset coordinate axis direction. By the method, the attitude angle of the single-axis downward derived model is calculated, and the derived model is cut by adopting different directions and different numbers of preset planes, so that the accuracy of the obtained attitude angle is ensured.
In one possible design, the clustering the slice group according to the target clustering manner to obtain a slice group includes:
clustering each slice surface in the slice surface group successively according to the target clustering mode, and judging whether difference data between the ith slice surface and the (i+1) th slice surface exceeds a preset difference data threshold value or not, wherein i is a positive integer;
If not, clustering the (i+1) th slice surface into the slice type same as the (i) th slice surface;
if yes, clustering the (i+1) th slice surface into a slice type different from the (i) th slice surface;
and taking all slice types of the slice surface group as slice class groups.
By the method, the slice groups are clustered successively according to the target clustering mode, the slice group corresponding to the slice group is determined, the purpose of classifying the slice group is achieved, and the accuracy of classifying the slice group is ensured.
In one possible design, the determining the simplified model corresponding to the slice group, processing the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model, includes:
calculating the minimum outer envelope corresponding to the slice group to obtain a simplified model, wherein the simplified model comprises at least one single unit component;
determining an overlapping part of the at least one single machine component in the simplified model, and deleting the overlapping part based on the target boundary optimization method to obtain a first simplified model;
and converting the first simplified model from the body coordinate system to the satellite coordinate system, and recombining the first simplified model under the satellite coordinate system to obtain a target model corresponding to the derived model.
By the method, the minimum outer envelope corresponding to the slice group is determined, the first simplified model is recombined under the satellite coordinate system, and the target model corresponding to the derived model is determined, so that the light weight processing of the derived model is realized.
In a second aspect, the present application provides a three-dimensional model lightweight device, the device comprising:
the acquisition module is used for acquiring a derived model and a satellite coordinate system corresponding to the derived model;
the conversion module is used for calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix and calculating a body coordinate system corresponding to the derived model;
the processing module is used for carrying out equidistant cutting on the derived model along the target direction in the body coordinate system to obtain a slice group, and clustering the slice group according to a target clustering mode to obtain a slice group;
and the simplifying module is used for determining a simplifying model corresponding to the slice group, and processing the simplifying model according to a target boundary optimizing method to obtain a target model corresponding to the derived model.
In one possible design, the conversion module is specifically configured to calculate an attitude angle of the derived model in each preset coordinate axis direction in the satellite coordinate system, obtain a plurality of attitude angles, screen out a target attitude angle with the highest occurrence frequency from all the attitude angles, and bring the target attitude angle into a preset rotation matrix, so as to calculate an ontology coordinate system corresponding to the derived model.
In one possible design, the conversion module is further configured to obtain an attitude angle of the derived model in a single preset coordinate axis direction in the satellite coordinate system, and includes the following steps: obtaining n planes, cutting the derived model along the m-th direction to obtain n cut sections, determining outer frames corresponding to the n cut sections, and determining the m-th attitude angle of the derived model in the single preset coordinate axis direction based on all the outer frames and the m-th direction, wherein n is 1 and 2, m is 1, 2 and 3, and the 1-th attitude angle, the 2-th attitude angle and the 3-th attitude angle are a plurality of attitude angles of the derived model in the single preset coordinate axis direction. In one possible design, the processing module is specifically configured to cluster each slice plane in the slice plane group successively according to the target clustering mode, determine whether difference data between an i-th slice plane and an i+1th slice plane exceeds a preset difference data threshold, if not, cluster the i+1th slice plane to be the same slice type as the i-th slice plane, if yes, cluster the i+1th slice plane to be a slice type different from the i-th slice plane, and use all slice types of the slice plane group as a slice type group.
In one possible design, the simplification module is specifically configured to calculate a minimum outer envelope corresponding to the slice group, obtain a simplified model, determine an overlapping portion of the at least one stand-alone component in the simplified model, delete the overlapping portion based on the target boundary optimization method, obtain a first simplified model, convert the first simplified model from the body coordinate system to the satellite coordinate system, and reorganize the first simplified model under the satellite coordinate system, so as to obtain a target model corresponding to the derived model.
In a third aspect, the present application provides an electronic device, including:
a memory for storing a computer program;
and the processor is used for realizing the three-dimensional model light weight method steps when executing the computer program stored in the memory.
In a fourth aspect, a computer readable storage medium has stored therein a computer program which, when executed by a processor, implements a three-dimensional model lightening method step as described above.
The technical effects of each of the first to fourth aspects and the technical effects that may be achieved by each aspect are referred to above for the technical effects that may be achieved by the first aspect or the various possible aspects of the first aspect, and are not repeated here.
Drawings
FIG. 1 is a flow chart of the three-dimensional model lightweight method steps provided herein;
FIG. 2 is a schematic view of the attitude angle of the derived model provided in the present application in the z-axis direction;
FIG. 3 is a schematic diagram of an ontology coordinate system of a derived model provided herein;
FIG. 4 is a schematic diagram of equidistant cutting of the derived model provided in the present application;
FIG. 5 is a schematic flow chart of a method for lightening a satellite structural model provided by the application;
fig. 6 is a schematic structural diagram of a three-dimensional model lightweight device provided in the present application;
fig. 7 is a schematic structural diagram of an electronic device provided in the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the present application will be described in further detail with reference to the accompanying drawings. The specific method of operation in the method embodiment may also be applied to the device embodiment or the system embodiment. It should be noted that "a plurality of" is understood as "at least two" in the description of the present application. "and/or", describes an association relationship of an association object, and indicates that there may be three relationships, for example, a and/or B, and may indicate: a exists alone, A and B exist together, and B exists alone. A is connected with B, and can be represented as follows: both cases of direct connection of A and B and connection of A and B through C. In addition, in the description of the present application, the words "first," "second," and the like are used merely for distinguishing between the descriptions and not be construed as indicating or implying a relative importance or order.
In the prior art, a model design software is adopted to derive an export model meeting simulation requirements from a satellite structure model, and as the three-dimensional data model of the satellite structure model has huge data volume, and the surface feature of each single component in the export model has high degree of refinement and complex local appearance detail, workers are required to manually process the export model for a plurality of times, so that a light model corresponding to the export model is obtained, the structure simplification process is complicated and a great deal of time is required to be consumed, and therefore, how to quickly determine the light model of the export model from the three-dimensional data model becomes the main problem to be solved at present.
Based on the above-described problems, embodiments of the present application provide a three-dimensional model lightening method to improve the efficiency of determining a lightening model of a derived model from a three-dimensional data model. The method and the device according to the embodiments of the present application are based on the same technical concept, and because the principles of the problems solved by the method and the device are similar, the embodiments of the device and the method can be referred to each other, and the repetition is not repeated.
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Referring to fig. 1, the application provides a three-dimensional model light-weight method, which can improve the efficiency of determining a light-weight model of a derived model from a three-dimensional data model, and the implementation flow of the method is as follows:
step S1: and obtaining a derived model and a satellite coordinate system corresponding to the derived model.
The satellite structure model is usually built based on model design software, which can be Creo software, and can be a structural model of an actual satellite or a structural model of a designed satellite, and because simulation of multiple physical fields such as electricity, magnetism, force, heat and the like only aims at part of the structural models in the satellite structure model, an export model in the satellite structure model needs to be disassembled based on the model design software, the export model usually comprises at least one single unit component, the surface feature of each single unit component has higher definition degree and complicated appearance details, and in order to avoid that the data volume of the export model is too huge, other simulation systems cannot read the export model, and the export model is subjected to light weight treatment.
First, a model design software needs to be based on a derived model conforming to simulation requirements and a satellite coordinate system of the derived model.
Step S2: and calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix, and calculating an ontology coordinate system corresponding to the derived model.
After determining the derived model and the satellite coordinate system of the derived model, in order to determine the target attitude angle of the derived model under the satellite coordinate system, the derived model needs to be cut according to a preset cutting mode, and the specific cutting process is as follows:
obtaining n planes, cutting a derived model along an mth direction to obtain n cutting sections, determining outer frames corresponding to the n cutting sections, determining an mth attitude angle of the derived model in the direction of a single preset coordinate axis based on all the outer frames and the mth direction, wherein n can be 1, 2 and 3, and the 1 st attitude angle, the 2 nd attitude angle and the 3 rd attitude angle are a plurality of attitude angles of the derived model in the direction of the single preset coordinate axis.
When n=1 and m=1, a plane is required to cut the derived model along a first direction to obtain a cut section, the plane is perpendicular to a single preset coordinate axis, the outer frames corresponding to the cut section are determined, the outer frames can be the minimum outer frames, and then a first attitude angle of the derived model in the direction of the single preset coordinate axis is determined based on the outer frames and the first direction.
When n=2 and m=2, two parallel planes are needed to cut the derived model along the second direction to obtain two cut sections, the two parallel planes are parallel to a single preset coordinate axis, the outer casing frame corresponding to each cut section is determined, the outer casing frame is the minimum outer casing frame, and the second attitude angle of the derived model in the direction of the single preset coordinate axis is determined based on the two outer casing frames and the second direction.
When n=2 and m=3, two parallel planes are required to cut the derived model along a third direction to obtain two cut sections, the two parallel planes are parallel to a single preset coordinate axis, the outer casing frame corresponding to each cut section is determined, the outer casing frame is the minimum outer casing frame, and a third attitude angle of the derived model in the direction of the single preset coordinate axis is determined based on the two outer casing frames and the third direction.
When n=1, m=2, or n=1, m=3, since a plane is cut to derive the model, and the plane is perpendicular to a single preset coordinate axis, all cases of n=1, m=2, or n=1, m=3 can refer to the description when n=1, m=1, and will not be described herein.
Based on the above-described steps, a first attitude angle, a second attitude angle and a third attitude angle of the derived model in a single preset coordinate axis direction can be determined, wherein the first attitude angle, the second attitude angle and the third attitude angle are a plurality of attitude angles of the derived model in the single preset coordinate axis direction.
Such as: if the horizontal axis of the satellite coordinate system is the x-axis, the vertical axis is the y-axis, and the vertical axis is the z-axis.
When the preset coordinate axis is the z axis, a schematic diagram of an attitude angle of the derived model in the z axis direction is shown in fig. 2, a preset plane perpendicular to the z axis is adopted to cut the derived model, a cut section is obtained, a minimum outer frame of the cut section is determined, an included angle between the minimum outer frame and the z axis is calculated, and the included angle is called a first attitude angle in the z axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the x-axis are required to be used for cutting the derived model, a first cutting section and a second cutting section are obtained, a first outer wrapping frame of the first cutting section and a second outer wrapping frame of the second cutting section are determined, the first outer wrapping frame is the minimum outer wrapping frame of the first cutting section, the second outer wrapping frame is the minimum outer wrapping frame of the second cutting section, then an included angle of the derived model in the z-axis direction is calculated according to the first outer wrapping frame and the second outer wrapping frame, and the included angle is the second attitude angle of the derived model in the z-axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the y axis are adopted to cut the derived model, a third cutting section and a fourth cutting section are obtained, a third outer wrapping frame of the third cutting section and a fourth outer wrapping frame of the fourth cutting section are determined, the third outer wrapping frame is the minimum outer wrapping frame of the third cutting section, the fourth outer wrapping frame is the minimum outer wrapping frame of the fourth cutting section, then an included angle of the derived model in the z axis direction is calculated according to the third outer wrapping frame and the fourth outer wrapping frame, and the included angle is formed into a third attitude angle of the derived model in the z axis direction.
Cutting the derived model for multiple times according to the method, obtaining multiple attitude angles of the derived model in the z-axis direction, counting the occurrence frequency of each attitude angle, screening out the attitude angle with the highest occurrence frequency, and calling the attitude angle with the highest occurrence frequency as the target attitude angle of the derived model in the z-axis direction.
When the preset coordinate axis is the y axis, a preset plane cutting derivation model perpendicular to the y axis is adopted to obtain a cutting section, a minimum outer wrapping frame of the cutting section is determined, an included angle between the minimum outer wrapping frame and the y axis is calculated, and the included angle is called as a first attitude angle in the y axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the x-axis are required to be used for cutting the derived model, a first cutting section and a second cutting section are obtained, a first outer wrapping frame of the first cutting section and a second outer wrapping frame of the second cutting section are determined, the first outer wrapping frame is the minimum outer wrapping frame of the first cutting section, the second outer wrapping frame is the minimum outer wrapping frame of the second cutting section, then an included angle of the derived model in the z-axis direction is calculated according to the first outer wrapping frame and the second outer wrapping frame, and the included angle is formed into a second attitude angle of the derived model in the y-axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the z-axis are adopted to cut the derived model, a third external wrapping frame of a third cutting section and a fourth external wrapping frame of the fourth cutting section are obtained, the third external wrapping frame is the minimum external wrapping frame of the third cutting section, the fourth external wrapping frame is the minimum external wrapping frame of the fourth cutting section, then an included angle of the derived model in the z-axis direction is calculated according to the third external wrapping frame and the fourth external wrapping frame, and the included angle is formed into a third attitude angle of the derived model in the y-axis direction.
Cutting the derived model for multiple times according to the method, obtaining multiple attitude angles of the derived model in the y-axis direction, counting the occurrence frequency of each attitude angle, screening out the attitude angle with the highest occurrence frequency, and calling the attitude angle with the highest occurrence frequency as the target attitude angle of the derived model in the y-axis direction.
When the preset coordinate axis is the x axis, a preset plane cutting derivation model perpendicular to the x axis is adopted to obtain a cutting section, a minimum outer wrapping frame of the cutting section is determined, an included angle between the minimum outer wrapping frame and the x axis is calculated, and the included angle is called as a first attitude angle in the x axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the y axis are required to be used for cutting the derived model, a first cutting section and a second cutting section are obtained, a first outer wrapping frame of the first cutting section and a second outer wrapping frame of the second cutting section are determined, the first outer wrapping frame is the minimum outer wrapping frame of the first cutting section, the second outer wrapping frame is the minimum outer wrapping frame of the second cutting section, then an included angle of the derived model in the z axis direction is calculated according to the first outer wrapping frame and the second outer wrapping frame, and the included angle is the second attitude angle of the derived model in the x axis direction.
In order to obtain the rotation parameters of the derived model in the satellite coordinate system, two preset planes which are parallel to each other and perpendicular to the y axis are adopted to cut the derived model, a third cutting section and a fourth cutting section are obtained, a third outer wrapping frame of the third cutting section and a fourth outer wrapping frame of the fourth cutting section are determined, the third outer wrapping frame is the minimum outer wrapping frame of the third cutting section, the fourth outer wrapping frame is the minimum outer wrapping frame of the fourth cutting section, then an included angle of the derived model in the z axis direction is calculated according to the third outer wrapping frame and the fourth outer wrapping frame, and the included angle is formed into a third attitude angle of the derived model in the x axis direction.
Cutting the derived model for multiple times according to the method, obtaining multiple attitude angles of the derived model in the x-axis direction, counting the occurrence frequency of each attitude angle, screening out the attitude angle with the highest occurrence frequency, and calling the attitude angle with the highest occurrence frequency as the target attitude angle of the derived model in the x-axis direction.
After determining the target attitude angles of the derived model in each preset coordinate axis direction, bringing the target attitude angles of each preset coordinate axis direction into a preset rotation matrix, and if the target attitude angles in the z-axis direction areThe target attitude angle in the y-axis direction is +.>The target attitude angle in the x-axis direction is +.>The preset rotation matrix is specifically as follows:
the target attitude angle in the z-axis direction, the target attitude angle in the y-axis direction and the target attitude angle in the x-axis direction are brought into the preset rotation matrix, so that the rotation angle of the derived model in the satellite coordinate system can be determined, the body coordinate system corresponding to the derived model can be calculated according to the rotation angle, the body coordinate system schematic diagram of the derived model is shown in fig. 3, and in fig. 3, the rotation angle of the derived model in the body coordinate system is 0.
Based on the method, the target attitude angle corresponding to the derived model is determined, so that the rotation angle of the derived model under the satellite coordinate system is determined, and the light weight processing efficiency of the derived model is improved.
Step S3: equidistant cutting is carried out on the derived model along the target direction in the body coordinate system to obtain a slice group, and clustering is carried out on the slice group according to the target clustering mode to obtain a slice group.
After determining the body coordinate system of the derived model, equidistant cutting is performed on the derived model along the target direction in the body coordinate system, a schematic diagram of equidistant cutting is shown in fig. 4, the target direction may be perpendicular to a certain coordinate axis in the body coordinate system, or the target direction may be adjusted according to actual situations, equidistant cutting is performed on the derived model, and a slice group corresponding to the derived model is obtained, which is not limited specifically herein.
After determining the slice group, in order to perform light weight processing on the derived model, the slice group needs to be clustered according to a target clustering mode, wherein the target clustering mode can adopt a Density clustering algorithm (English full name: density-Based Spatial Clustering of Applications with Noise, abbreviated as DBSCAN) to cluster slice planes, and can also select a clustering mode according to actual clustering requirements, and the clustering mode is not excessively described herein.
In the embodiment of the application, a small clustering radius can be set to cluster the slice surface group, a single unit component corresponding to clustered noise vertex data is output, vertex data which is gathered into one type in the noise vertex data is discarded as a protruding part, and the protruding part can be a pin, an exposed cable, a protruding screw, a plug-in unit and the like, so that the slice surface group with the pin outer envelope removed is obtained.
In order to classify the slice planes, each slice plane in the slice plane group needs to be clustered successively according to a target clustering mode, and the specific clustering process is as follows:
after clustering the slice group, obtaining clustering data of each slice, comparing slice data of each adjacent slice, determining difference data between each adjacent slice, judging whether the difference data between the ith slice and the (i+1) th slice exceeds a preset difference data threshold, wherein i can be 1, 2, 3, 4 and 5 … …, and when the difference data between the ith slice and the (i+1) th slice exceeds the preset difference data threshold, representing that the difference between the ith slice and the (i+1) th slice is larger, classifying the (i+1) th slice and the (i) th slice into different slice types; when the difference data between the ith slice surface and the (i+1) th slice surface does not exceed the preset difference data threshold value, the difference between the ith slice surface and the (i+1) th slice surface is smaller, and the ith slice surface and the (i+1) th slice surface can be classified into the same slice type, so that classification of each slice surface is realized, and the classification of each slice surface is used as a slice class group, namely: the slice class group may include all slice types.
Based on the method, after equidistant cutting is carried out on the derived model, the slice groups are clustered according to the target clustering mode, so that the slice group is obtained, the integrity of the slice surfaces corresponding to the derived model and the integrity of slice surface classification are ensured, and the light weight efficiency of the derived model is improved.
Step S4: and determining a simplified model corresponding to the slice group, and processing the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model.
In order to ensure that a simplified model of an derived model is obtained, after obtaining a slice group, the embodiment of the present application may calculate a minimum outer envelope corresponding to a slice group corresponding to the slice group by adopting an OBB bounding box, and use a model corresponding to the minimum outer envelope as the simplified model of the derived model, where the simplified model includes at least one stand-alone component.
Because the simplified model includes at least one single component, overlapping parts inevitably exist between the single component and the single component or between parts in the single component after slicing and clustering, interference is generated in the simulation process, therefore, the overlapping parts between the single components in the simplified model need to be determined, the method for determining the overlapping parts can be a boolean operation method, and then the overlapping parts are deleted according to a target boundary optimization method, so as to obtain a first simplified model corresponding to the simplified model.
Since the equidistant segmentation, clustering and the like of the derived model are performed based on the body coordinate system, in order to make the derived model coincide with the coordinate system of the first simplified model, the first simplified model in the body coordinate system needs to be converted into the satellite coordinate system, and the first simplified model is recombined under the satellite coordinate system to obtain the target model corresponding to the derived model, so that the light-weight model corresponding to the derived model is obtained.
It should be noted that, in this embodiment of the present application, a flow chart of a satellite structural model light-weight method is provided, referring to fig. 5 and 501, an export model is input, the export model is a single machine or a structural component, 502 determines a cutting direction of the export model, 503 performs equidistant cutting on the export model, 504 and clusters a slice group, and removes pins, exposed cables, and the like, 505 obtains a slice group, in order to classify the slice group, 506 performs slice-by-slice clustering, 507 determines whether difference data between adjacent slice surfaces exceeds a preset difference data threshold, if the difference data exceeds the preset difference data threshold, a last slice surface detected currently is used as a start point of re-clustering, and a clustering result of the last slice surface is inconsistent; if the difference data does not exceed the preset difference data threshold value, the detected adjacent slice surfaces are used as a class; 508, obtaining a slice group after detecting all slice groups, 509 again calculating the minimum outer envelope of the slice group, 510 when detecting that the export model is not processed, equally cutting the partial export model which is not processed, and repeating the processing flow; when it is detected that all processes of deriving the model are completed, the first simplified model is reassembled 511 to obtain the target model.
Based on the method, the derived model in the satellite structure model is disassembled, light-weight processed and boundary optimized, and the target model is prevented from being obtained by adopting manual processing for multiple times, so that the efficiency of determining the target model is improved.
Based on the same inventive concept, the embodiment of the present application further provides a three-dimensional model light-weight device, where the three-dimensional model light-weight device is configured to implement a function of a three-dimensional model light-weight method, and referring to fig. 6, the device includes:
the obtaining module 601 is configured to obtain a derived model and a satellite coordinate system corresponding to the derived model;
the conversion module 602 is configured to calculate a target attitude angle of the derived model in the satellite coordinate system based on a preset cutting manner, and introduce the target attitude angle into a preset rotation matrix, so as to calculate a body coordinate system corresponding to the derived model;
the processing module 603 is configured to perform equidistant cutting on the derived model in the body coordinate system along a target direction to obtain a slice group, and cluster the slice group according to a target clustering manner to obtain a slice group;
and a simplifying module 604, configured to determine a simplified model corresponding to the slice group, and process the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model.
In one possible design, the conversion module 602 is specifically configured to calculate an attitude angle of the derived model in each preset coordinate axis direction in the satellite coordinate system, obtain a plurality of attitude angles, screen out a target attitude angle with the highest appearance frequency from all the attitude angles, and take the target attitude angle into a preset rotation matrix, so as to calculate an ontology coordinate system corresponding to the derived model.
In one possible design, the conversion module 602 is further configured to obtain an attitude angle of the derived model in a single preset coordinate axis direction in the satellite coordinate system, where the method includes the following steps: obtaining n planes, cutting the derived model along the m-th direction to obtain n cut sections, determining outer frames corresponding to the n cut sections, and determining the m-th attitude angle of the derived model in the single preset coordinate axis direction based on all the outer frames and the m-th direction, wherein n is 1 and 2, m is 1, 2 and 3, and the 1-th attitude angle, the 2-th attitude angle and the 3-th attitude angle are a plurality of attitude angles of the derived model in the single preset coordinate axis direction.
In one possible design, the processing module 603 is specifically configured to cluster each slice plane in the slice plane group sequentially according to the target clustering manner, determine whether difference data between an i-th slice plane and an i+1th slice plane exceeds a preset difference data threshold, if not, cluster the i+1th slice plane to be the same slice type as the i-th slice plane, if yes, cluster the i+1th slice plane to be a slice type different from the i-th slice plane, and use all slice types of the slice plane group as a slice group.
In one possible design, the simplifying module 604 is specifically configured to calculate a minimum outer envelope corresponding to the slice group, obtain a simplified model, determine an overlapping portion of the at least one stand-alone component in the simplified model, delete the overlapping portion based on the target boundary optimization method, obtain a first simplified model, convert the first simplified model from the body coordinate system to the satellite coordinate system, and reconstruct the first simplified model under the satellite coordinate system, so as to obtain the target model corresponding to the derived model.
Based on the same inventive concept, the embodiment of the present application further provides an electronic device, where the electronic device may implement the function of the foregoing three-dimensional model light-weight device, and referring to fig. 7, the electronic device includes:
at least one processor 701, and a memory 702 connected to the at least one processor 701, in this embodiment of the present application, a specific connection medium between the processor 701 and the memory 702 is not limited, and in fig. 7, the processor 701 and the memory 702 are connected by a bus 700 as an example. Bus 700 is shown in bold lines in fig. 7, and the manner in which the other components are connected is illustrated schematically and not by way of limitation. The bus 700 may be divided into an address bus, a data bus, a control bus, etc., and is represented by only one thick line in fig. 7 for convenience of representation, but does not represent only one bus or one type of bus. Alternatively, the processor 701 may be referred to as a controller, and the names are not limited.
In the embodiment of the present application, the memory 702 stores instructions executable by the at least one processor 701, and the at least one processor 701 can execute a three-dimensional model lightening method as described above by executing the instructions stored in the memory 702. The processor 701 may implement the functions of the various modules in the apparatus shown in fig. 6.
The processor 701 is a control center of the apparatus, and may connect various parts of the entire control device using various interfaces and lines, and by executing or executing instructions stored in the memory 702 and invoking data stored in the memory 702, various functions of the apparatus and processing data, thereby performing overall monitoring of the apparatus.
In one possible design, processor 701 may include one or more processing units, and processor 701 may integrate an application processor and a modem processor, wherein the application processor primarily processes operating systems, user interfaces, application programs, and the like, and the modem processor primarily processes wireless communications. It will be appreciated that the modem processor described above may not be integrated into the processor 701. In some embodiments, processor 701 and memory 702 may be implemented on the same chip, or they may be implemented separately on separate chips in some embodiments.
The processor 701 may be a general purpose processor such as a Central Processing Unit (CPU), digital signal processor, application specific integrated circuit, field programmable gate array or other programmable logic device, discrete gate or transistor logic device, discrete hardware components, which may implement or perform the methods, steps, and logic blocks disclosed in embodiments of the present application. The general purpose processor may be a microprocessor or any conventional processor or the like. The steps of a three-dimensional model light-weight method disclosed in connection with the embodiments of the present application may be directly embodied as a hardware processor executing, or may be executed by a combination of hardware and software modules in the processor.
The memory 702 is a non-volatile computer-readable storage medium that can be used to store non-volatile software programs, non-volatile computer-executable programs, and modules. The Memory 702 may include at least one type of storage medium, and may include, for example, flash Memory, hard disk, multimedia card, card Memory, random access Memory (Random Access Memory, RAM), static random access Memory (Static Random Access Memory, SRAM), programmable Read-Only Memory (Programmable Read Only Memory, PROM), read-Only Memory (ROM), charged erasable programmable Read-Only Memory (Electrically Erasable Programmable Read-Only Memory), magnetic Memory, magnetic disk, optical disk, and the like. Memory 702 is any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited to such. The memory 702 in the embodiments of the present application may also be circuitry or any other device capable of implementing a memory function for storing program instructions and/or data.
By programming the processor 701, the code corresponding to the three-dimensional model weight reduction method described in the foregoing embodiment can be cured into the chip, so that the chip can execute the three-dimensional model weight reduction step of the embodiment shown in fig. 1 during operation. How to design and program the processor 701 is a technology well known to those skilled in the art, and will not be described in detail herein.
Based on the same inventive concept, the embodiments of the present application also provide a storage medium storing computer instructions that, when executed on a computer, cause the computer to perform a three-dimensional model weight reduction method as previously discussed.
In some possible embodiments, the aspects of a three-dimensional model lightening method may also be implemented in the form of a program product comprising program code for causing a control apparatus to carry out the steps of a three-dimensional model lightening method according to the various exemplary embodiments of the application as described herein above when the program product is run on a device.
It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various modifications and variations can be made in the present application without departing from the spirit or scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims and the equivalents thereof, the present application is intended to cover such modifications and variations.
Claims (10)
1. A method for lightening a three-dimensional model, comprising:
obtaining a derived model and a satellite coordinate system corresponding to the derived model;
calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix, and calculating a body coordinate system corresponding to the derived model;
Equidistant cutting is carried out on the derived model along the target direction in the body coordinate system to obtain a slice group, and the slice group is clustered according to a target clustering mode to obtain a slice group;
and determining a simplified model corresponding to the slice group, and processing the simplified model according to a target boundary optimization method to obtain a target model corresponding to the derived model.
2. The method of claim 1, wherein the calculating a target attitude angle of the derived model in the satellite coordinate system based on the preset cutting mode, bringing the target attitude angle into a preset rotation matrix, and calculating an ontology coordinate system corresponding to the derived model, includes:
calculating the attitude angles of the derived model in each preset coordinate axis direction in the satellite coordinate system to obtain a plurality of attitude angles;
and screening out the target attitude angle with the highest appearance frequency from all the attitude angles, taking the target attitude angle into a preset rotation matrix, and calculating a body coordinate system corresponding to the derived model.
3. The method of claim 2, wherein said calculating attitude angles of the derived model in each preset coordinate axis direction in the satellite coordinate system, obtaining a plurality of attitude angles, comprises:
Acquiring the attitude angle of the derived model in the direction of a single preset coordinate axis in the satellite coordinate system, wherein the attitude angle comprises the following steps:
obtaining n planes, cutting the derived model along the m-th direction to obtain n cut sections, determining outer frames corresponding to the n cut sections, and determining the m-th attitude angle of the derived model in the single preset coordinate axis direction based on all the outer frames and the m-th direction, wherein n is 1 and 2, m is 1, 2 and 3, and the 1-th attitude angle, the 2-th attitude angle and the 3-th attitude angle are a plurality of attitude angles of the derived model in the single preset coordinate axis direction.
4. The method of claim 1, wherein clustering the slice groups according to the target clustering method to obtain slice groups comprises:
clustering each slice surface in the slice surface group successively according to the target clustering mode, and judging whether difference data between the ith slice surface and the (i+1) th slice surface exceeds a preset difference data threshold value or not, wherein i is a positive integer;
if not, clustering the (i+1) th slice surface into the slice type same as the (i) th slice surface;
If yes, clustering the (i+1) th slice surface into a slice type different from the (i) th slice surface;
and taking all slice types of the slice surface group as slice class groups.
5. The method of claim 1, wherein determining the simplified model corresponding to the slice group, and processing the simplified model according to a target boundary optimization method to obtain the target model corresponding to the derived model, comprises:
calculating the minimum outer envelope corresponding to the slice group to obtain a simplified model, wherein the simplified model comprises at least one single unit component;
determining an overlapping part of the at least one single machine component in the simplified model, and deleting the overlapping part based on the target boundary optimization method to obtain a first simplified model;
and converting the first simplified model from the body coordinate system to the satellite coordinate system, and recombining the first simplified model under the satellite coordinate system to obtain a target model corresponding to the derived model.
6. A three-dimensional model lightweight device, comprising:
the acquisition module is used for acquiring a derived model and a satellite coordinate system corresponding to the derived model;
The conversion module is used for calculating a target attitude angle of the derived model under the satellite coordinate system based on a preset cutting mode, bringing the target attitude angle into a preset rotation matrix and calculating a body coordinate system corresponding to the derived model;
the processing module is used for carrying out equidistant cutting on the derived model along the target direction in the body coordinate system to obtain a slice group, and clustering the slice group according to a target clustering mode to obtain a slice group;
and the simplifying module is used for determining a simplifying model corresponding to the slice group, and processing the simplifying model according to a target boundary optimizing method to obtain a target model corresponding to the derived model.
7. The apparatus of claim 6, wherein the conversion module is specifically configured to calculate an attitude angle of the derived model in each preset coordinate axis direction in the satellite coordinate system, obtain a plurality of attitude angles, screen out a target attitude angle with a highest occurrence frequency from all the attitude angles, and bring the target attitude angle into a preset rotation matrix, so as to calculate an ontology coordinate system corresponding to the derived model.
8. The apparatus of claim 7, wherein the conversion module further configured to obtain an attitude angle of the derived model in a single preset coordinate axis direction in the satellite coordinate system comprises the steps of: obtaining n planes, cutting the derived model along the m-th direction to obtain n cutting sections, determining outer frames corresponding to the n cutting sections, and determining the m-th attitude angle of the derived model in the single preset coordinate axis direction based on all the outer frames and the m-th direction.
9. An electronic device, comprising:
a memory for storing a computer program;
a processor for carrying out the method steps of any one of claims 1-5 when executing a computer program stored on said memory.
10. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored therein a computer program which, when executed by a processor, implements the method steps of any of claims 1-5.
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